Cast casing treatment for compressor blades

A tip shroud assembly for an axial flow gas turbine engine, said tip shroud assembly comprising

• an annular shroud extending circumferentially about a reference axis, said shroud including a plurality of arcuate segments, each segment comprising
• a first arcuate member, a second arcuate member, and a third arcuate member interposed between said first and second arcuate members, said third arcuate member in spaced relation to said first arcuate member defining a first gap therebetween, said third arcuate member in spaced relation to said second arcuate member defining a second gap therebetween, each of said arcuate members having a radially inner surface facing said reference axis and a radially outer surface facing away from said reference axis, and said radially inner surface of said third arcuate member substantially defines a section of a cone,
• a backing sheet, said backing sheet spanning between the first and second arcuate members and sealingly secured to the radially outer surfaces thereof, said backing sheet in spaced relation to the radially outer surface of said third arcuate member, and
• a plurality of vane walls, each vane wall integral with said first, second and third arcuate members, each vane wall having a first end and a second end, said first end of each vane wall spanning the first gap thereby connecting the radially inner surfaces of the first and third arcuate members, and said second end of each vane wall spanning the second gap thereby connecting the radially inner surfaces of the second and third arcuate members.